Accident Overview
On April 22, 2024, about 1826 central daylight time, a Lancair Legacy FG airplane (N550NL) was destroyed in an accident near Spicewood, Texas. The pilot was fatally injured. The flight was conducted as a Title 14 Code of Federal Regulations Part 91 personal flight.
Flight Details
Automatic Dependent Surveillance-Broadcast data indicated that the accident flight was the second flight of the day. The airplane departed Garner Field Airport (UVA), Uvalde, Texas, about 1721 and was destined for Spicewood Airport (88R), Spicewood, Texas. The airplane overflew the airport and entered a left traffic pattern for runway 17.
Witness Account
A witness reported that during the first approach to land, the airplane was “fast” and “ballooned.” A wind gust was present at the time, and the pilot initiated a go-around. On the second approach, the nose landing gear nearly struck the runway before the airplane banked to the left. The witness heard the engine increase in power, observed the airplane climb “straight up,” yaw to the left, and then descend “straight down.”
Accident Site and Wreckage
The accident site was located in a wooded area about 350 feet east of the runway. The airplane impacted the ground on a 125° magnetic heading and came to rest in an upright position on about a 210° magnetic heading, approximately 20 feet from its initial point of impact. Portions of the airframe were consumed by a postimpact fire. All major components of the airplane were present at the accident site.
Control System Examination
The aileron and elevator push-pull control tubes were consumed by fire. The right rudder control cable remained attached to the rudder pedal assembly and was continuous to the rudder bellcrank. The left rudder control cable remained attached to the rudder bellcrank, but impact separated it from the rudder pedal assembly.
Engine and Propeller Examination
The engine came to rest inverted and exhibited impact and thermal damage. Borescope examination of the cylinders revealed no anomalies. The crankshaft was rotated via an accessory gear drive. Crankshaft, camshaft, and valvetrain continuity were confirmed to the rear accessory section of the engine, and thumb compression and suction were attained on all four cylinders. Thermal damage precluded field testing of the ignition system. No anomalies were noted during the examination of the fuel system.
The propeller was impact separated from the engine. Both propeller blades exhibited chordwise abrasions, leading edge gouges, and longitudinal twisting. Torsional deformation was noted to the propeller spinner.
Further Examination
The wreckage was retained for further examination.